org.vizzini.math.orbit
Class ParabolicOrbit

java.lang.Object
  org.vizzini.math.orbit.AbstractOrbit
      org.vizzini.math.orbit.ParabolicOrbit

All Implemented Interfaces:

IOrbit

public class ParabolicOrbit
extends AbstractOrbit

Provides a parabolic orbit.

Since:

v0.3

Version:

v0.3

Author:

Jeffrey M. Thompson

Constructor Summary

ParabolicOrbit(double mu, double a, double i, double omega, double w, double trueAnomaly0)
Construct this object using the given parameters.

ParabolicOrbit(double mu, double a, double i, double omega, double w, double trueAnomaly0, double t0)
Construct this object using the given parameters.

ParabolicOrbit(double mu, Vector r, Vector v)
Construct this object using the given parameters.

ParabolicOrbit(double mu, Vector r, Vector v, double t0)
Construct this object using the given parameters.

Method Summary

Methods inherited from class org.vizzini.math.orbit.AbstractOrbit

getA, getE, getEcc, getEccentricAnomaly, getEccentricAnomaly0, getH, getI, getMeanAnomaly, getMeanAnomaly0, getMu, getN, getOmega, getPeriod, getR, getR0, getRa, getRp, getT0, getTrueAnomaly, getTrueAnomaly0, getV, getV0, getVa, getVp, getW, isVectorBased, setA, setEcc, setI, setMu, setOmega, setR0, setT0, setTrueAnomaly0, setV0, setW, toString

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, wait, wait, wait

Constructor Detail

ParabolicOrbit

public ParabolicOrbit(double mu,
                      Vector r,
                      Vector v)

Construct this object using the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

r - Position vector. (km)

v - Velocity vector. (km/sec)

Since:

v0.3

ParabolicOrbit

public ParabolicOrbit(double mu,
                      Vector r,
                      Vector v,
                      double t0)

Construct this object using the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

r - Position vector. (km)

v - Velocity vector. (km/sec)

t0 - Epoch time of parameters. (sec)

Since:

v0.3

ParabolicOrbit

public ParabolicOrbit(double mu,
                      double a,
                      double i,
                      double omega,
                      double w,
                      double trueAnomaly0)

Construct this object using the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

a - Semi-major axis. (km)

i - Inclination. (radians)

omega - Longitude of the ascending node. (radians)

w - Argument of periapsis. (radians)

trueAnomaly0 - True anomaly at epoch. (radians)

Since:

v0.3

ParabolicOrbit

public ParabolicOrbit(double mu,
                      double a,
                      double i,
                      double omega,
                      double w,
                      double trueAnomaly0,
                      double t0)

Construct this object using the given parameters.

Parameters:

mu - Gravitational parameter of central body. (km^3 sec^-2)

a - Semi-major axis. (km)

i - Inclination. (radians)

omega - Longitude of the ascending node. (radians)

w - Argument of periapsis. (radians)

trueAnomaly0 - True anomaly at epoch. (radians)

t0 - Epoch time of parameters. (sec)

Since:

v0.3